Adaptive pressure control experiment: Controller design and implementation

Alan, Anıl; Yıldız, Yıldıray; Poyraz, Umit

doi:10.1109/ccta.2017.8062444

Cited by 7 publications

(6 citation statements)

References 6 publications

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“…Additionally, using the characteristics, it can be extended to a multi-nozzle system for divert and attitude control as a reaction control system (RCS), so a simulation model was also developed considering each nozzle throat area, and various control systems were designed through the simulation approach [85][86][87][88][89][90][91]. Furthermore, recently, by applying a VTSRM, a simulation model of the ramjet or scramjet system, called dual-mode ramjet (DMRJ) or solid-fuel rocket scramjet (SFRSCRJ), has been developed and studied as a gas generator to generate and control the fuel-rich combustion gas, as in Figure 6 [92]. Since the fuel-rich combustion gas, generated from a VTSRM, is controlled by the pintle and makes variable thrust in the ram combustor, the characteristics of the system drive are one of several challenges in the DMRJ or SFRSCRJ, so a simulation model of SPRMs has been conducted to design an accurate control system for combustion gas flow rate [92][93][94][95].…”

Section: Solid-propellant Rocket Motormentioning

confidence: 99%

Numerical Simulation of Chemical Propulsion Systems: Survey and Fundamental Mathematical Modeling Approach

Cha

2023

Aerospace

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This study deals with the mathematical modeling and numerical simulation of chemical propulsion systems (CPSs). For this, we investigate and summarize a comprehensive collection of the simulation modeling developments of CPSs in academic works, applications, and industrial fields. Then, we organize and analyze the simulation modeling approaches in several ways. After that, we organize differential-algebraic Equations (DAEs) for fundamental mathematical modeling consisting of the governing Equations (ordinary differential equations, ODEs) for the components and other equations derived from several physical rules or characteristics (algebraic equations or phenomenological equations, AEs) and then synthesize and summarize the fundamental structures of analytic mathematical modeling by types (liquid-propellant rocket engines, solid-propellant rocket motors, and hybrid-propellant rocket motors) of CPSs.

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Section: Solid-propellant Rocket Motormentioning

confidence: 99%

Numerical Simulation of Chemical Propulsion Systems: Survey and Fundamental Mathematical Modeling Approach

Cha

2023

Aerospace

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“…8 Recently, scholars have assigned great significance to gas flow control and therefore have conducted several studies on its control strategy. For instance, Alan et al 9,10 developed a model reference adaptive controller (MRAC) to regulate the pressure of the gas generator and verified the performance of the MRAC via simulations with cold gas and air. Niu et al 11 implemented a proportionalintegral controller based on a linear matrix inequality for gas flow regulation systems, and the effectiveness of the system was verified via experiments.…”

Section: Introductionmentioning

confidence: 99%

Model predictive control–based compound control strategy for ducted rockets gas flow with anti-regulation suppression

Zhang

Zeng

Wang

et al. 2023

Proceedings of the Institution of Mechanical Engineers, Part G:

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Variable flow ducted rockets are excellent candidates for propulsion systems in hypersonic vehicles. However, the anti-regulation characteristics of the gas flow not only decrease the stability of ducted rockets but also create difficulties in the control system design. In this study, a model predictive control (MPC)–based compound control algorithm that suppresses the anti-regulation is proposed. First, a mathematical model involving a gas flow regulation system was developed to describe and analyse the anti-regulation. Next, a fused feedback variable that included both the gas flow and the gas generator pressure signal was constructed. An MPC control system with the fused feedback variable was also designed. Then, to accurately predict the gas flow and the anti-regulation, a nonlinear disturbance observer was constructed. To evaluate the performance of the controller, two scenarios that were regulated by a tracking differentiator proportional–integral–derivative controller and a model reference adaptive control controller were constructed and compared. The theoretical results demonstrate that the proposed method exhibited a superior performance compared to previous methods by overcoming the supposed trade-off between the response rate and the anti-regulation of gas flow systems.

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“…Furthermore, these days, using these characteristics, the ramjet or scramjet system, called dual-mode ramjet (DMRJ) or solid-fuel rocket scramjet (SFRSCRJ), has been developed and studied as in Figure 2 [8][9][10][11]. The fuel-rich combustion gas, generated from the solid propellant system, is controlled by the pintle, and it makes variable thrust in the ram combustor.…”

Section: Introductionmentioning

confidence: 99%

“…Therefore, for effective pressure and thrust control of a VTSRM, it is essential to design the control algorithms considering the nonlinearity and uncertainty [13]. For these reasons, many studies have been carried out to solve the issues keeping these advantages of VTSRM, focusing on several concepts: control of thrust and combustion pressure [13][14][15][16], a reaction control system (RCS) composed of multiple nozzles for divert and attitude control [17][18][19][20], the flow characteristics by pintle shape using computational fluid dynamics (CFD) [21][22][23][24], the experiment using cold or hot gas [25,26], and a part of ramjet or scramjet to generate and control the fuel-rich combustion gas [8][9][10][11].…”

Section: Introductionmentioning

confidence: 99%

Performance Comparison of Control Strategies for a Variable-Thrust Solid-Propellant Rocket Motor

Cha

Oliveira

2022

Aerospace

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This paper deals with a performance comparison of the control algorithm for a variable-thrust solid-propellant rocket motor (VTSRM). To do this, we develop a simulation model of a VTSRM considering characteristic changes in the combustor and design control systems for pressure and thrust. We use three types of control algorithms for the pressure control: classical PID control, feedback linearization control, and fuzzy PID control, and two control algorithms for thrust control: classical PID control and fuzzy PID control. Finally, we compare the performance of each control system through a numerical simulation using step responses. Through this work, we check that feedback linearization is better in pressure control, and fuzzy PID control is more appropriate in thrust control. Especially using fuzzy PID control, we can get fast settling with a small undershoot even if the system is a nonminimum phase system.

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Adaptive pressure control experiment: Controller design and implementation

Cited by 7 publications

References 6 publications

Numerical Simulation of Chemical Propulsion Systems: Survey and Fundamental Mathematical Modeling Approach

Numerical Simulation of Chemical Propulsion Systems: Survey and Fundamental Mathematical Modeling Approach

Model predictive control–based compound control strategy for ducted rockets gas flow with anti-regulation suppression

Performance Comparison of Control Strategies for a Variable-Thrust Solid-Propellant Rocket Motor

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